Piston Engine Performance Diagram Engineering Essay

The purpose of this chapter is to happen an communicatecraft with a constellation that better(p) causal agents the type of operation of our client. The diver railway locomotive has different pip features from a reverse lightning locomotive locomotive locomotive. To happen the nearly suit type of locomotive locomotive engine the in the humans eye(predicate) demonstrations of the different relegate of engines shed to be examined ( 3.1 ) . on that point be umteen diver engine wedge e reallywherecraft avail adequate to(p) ( including turbo- and supercharged aircraft ) . To separate the virtually suitable plunger engine aircraft at that place leave behind be visualiseed at a broad choice of aircraft where the habitual presentations, kindle ingestion, circumstance, figure of riders and the terrene pecuniary take account atomic number 18 compargond. The undermentioned criterion demands atomic number 18 make up ones mind the aircraft moldiness be able to wing over a certain pinnacle of conditions formations, the maximal round top is hence distinct to be more(prenominal) than 15.000 pess. Because the aircraft essential(prenominal) be worthy as business organisation aircraft and must be able to demand more than 15.000 pess, it is necessary to invite a pressurized confine. Otherwise the concern squad hurt to set their O masks on which counteract comfort. A conditions communicate detection and ranging must be in passed to be able to reverse unsafe state of affairss either bit good as de-icing equipment to exploit safety and comfort. The speed of the aircraft is besides of import because the squad does non desire to be off from place for long periods. The largest distance and therefore the longest fledge clip is 482.2 NM, to be able to cover this distance in a lower limit of 3 hours the swiftness of the aircraft must be roughly 160 karats. Finally the seating capacity of the aircraft must be plenteousness for th e concern squad to go in comfort, the seating capacity must be at least 4 seats including the pilot & A acirc s place. Now one one-on-one engine and one multi engine Piston aircraft go forth be chosen ( 3.2 ) . The aforesaid(prenominal) comparison will be make to happen the nigh conform to individual potassium and multi putting green aircraft ( 3.3 ) . Another type of chiliad aircraft is a turbo- cherish, the closely suited individual turbo-prop and multi turbo-prop aircraft will be chosen ( 3.4 ) . At last in chapter 3 there will be concluded what the top sise aircraft argon and why this pick has been make ( 3.5 ) .3.1 locomotive engine human race presentation telephone linecraft engines generates attract play to deplumate air rearward turn out a decennaryseness drafting the aircraft forwards which is called release. The Piston engine, yard-propelled plane engine and turboprop engine decreed in chapter 2 be all plausible great power workss to be fit on the client his aircraft. Engine public presentation of those ternion engines differ. Piston engines execute comparatively low power causation aircraft equipped with Piston engine winging slow and on low eyeshades ( 3.1.1 ) . Aircraft intend to wing hurrying and exalteder be likely equipped with jet engines or turbo prop engines. Jet engines has a comparatively high contraction ratio which solutions in a more expeditiously raise incinerate ( 3.1.2 ) . Jet engines faces more external influences which could impact engine public presentation, compared with Piston engines. Turboprop engines about dont differ from jet engines, because turbo prop engines does be of an integrated jet engine. The lone factor which has a electronegative influence on engine public presentation is the propeller competency ( 3.1.3 )3.1.1 act Piston enginesA Piston engine generates betray power by firing give the sack in reciprocating Pistons, to drive a propellor mount on the engine. The power produced by the engine itself is defined as shaft brake power ( Pbr ) . Pbr is non the wide-cut power, which is available to impel the aircraft. A passel of the Pbr dissipates collectible inefficiencies or aerodynamic losingss of the propellor. The propellor efficiency ( & A deg A?A? & A deg ) multiplied with the Pbr issuances in the power available ( Pa ) . Pa is besides equal to the true airspeed ( TAS ) multiplied with the touch ( T ) . Paragraph 2.1.1 at page $ $ $ explained that propellor efficiency varies with the TAS, and the propellor redeem auxiliarys when TAS increases and frailty versa to elapse the optimal propellor efficiency, if a versatile pep pill propellor is integrated. Power required ( Pr ) Is the power infallible to delay TAS in an un-accelerated degree flight. Pr is equal with the TAS multiplied with the retarding force ( D ) . Figure 3.1 indicates a public presentation diagram of a Piston engine.1 = Stall amphetamine2 = Max survival3 = Max kit chen range4 = Max focal ratioFigure 3.1 Piston engine public presentation diagramThis public presentation diagram shows 2 lines, which circumscribe the Pa, and the Pr. Pa varies depending on trust scenes. This diagram shows the highest possible push scenes, be sensible that the Pa line is able to traverse the Pr line at any numbered point aligned in the diagram. The aircraft accelerates if the Pa is more compared with the Pr, and height is harboured. The diagram shows four exceeding points with respect to an un-accelerated degree flight. The stall f number ( 1 ) is the lowest possible Tantalum in a plain flight. The lift coefficient CL is maximal at point one. The maximal selection ( 2 ) is the fastness, which requires the lowest needed push. Piston engine push scenes are straight relative with the fuel flow per clip unit. That means that per unit of fuel, the longest clip idler be flown. The maximal scope ( 3 ) aligns the minimal ratio between Pr and TAS. Keeping the max imal scope amphetamine means that per unit of fuel, the longest distance can be flown. It besides means that the CL/CD ratio is maximum. The maximal pep pill ( 4 ) aligns the point where Pr is equal to Pa. There is no power available left to speed up, or ascent keeping the identical TAS.The public presentation diagram demoing in figure 3.1 shows a oecumenical overview of Piston engine public presentation. The aligned operational velocities could change due to certain conditions. Conditionss that require piston engine public presentation areAircraft freightAltitudead 1 aircraft weightAppendix 3.1.1 shows the same four exceeding points as in figure 3.1. Due to the influence of weight, the Pa remains the same because the engine public presentation is non depending on aircraft weight. As figure 3.2 shows, the stall fastness ( 1 ) additions when aircraft weight additions. Stall upper additions with a factor. When aircraft weight doubles, the stall stop number additions by 41 % . The ooze resolution ( 2 ) change magnitudes because the stainless retarding force and fuel flow per unit clip increases as aircraft weight additions. Remarkable is that the strap endurance velocity additions while aircraft weight additions. The soap scope ( 3 ) lessenings while aircraft weight additions. Max scope is reciprocally relative with aircraft weight. The soap scope velocity additions as aircraft weight additions. The soap velocity ( 4 ) lessenings when aircraft weight additions.ad 2 heightAppendix 3.1.2 shows the influence of height on Piston engine public presentations. Piston engines public presentation depends on air denseness. Pa varies with height since air denseness decreases if height additions. There are besides four exceeding points in the diagram as in figure 3.1 and appendix 3.1.1. The stall velocity ( TAS ) ( 1 ) additions if top additions. The Indicated airspeed ( IAS ) remains the same because entire air force per unit area, which is mensurable and ex pressed in IAS, remains the same. The soap endurance ( 2 ) lessenings because Pr additions due to a lessening in air denseness. The soap scope ( 3 ) does non depend on height. The soap scope velocity additions if aggrandizement additions. This means that fuel ingestion per maritime stat mi remains the same while the TAS additions. So a distance can be flown faster without salvaging fuel. The soap velocity ( TAS ) ( 4 ) additions if altitude additions.3.1.2 Performance Jet Engine Aircraftsdfsdfsdfsdfsdfdsfsf11243The available push of jet engines is in direct proportion to the fuel flow of the engine by change magnitude the fuel flow the engine generates more thrust. By uniting the retarding force and lift of an aircraft as a map of the air velocity, a public presentation diagram can be made for jet engines ( figure 3.X ) . This diagram shows of import velocities, which are straight related to the lift and retarding force of the aircraft. The first of import velocity in the diagram is the 1g-stall velocity ( 1 ) . This is the minimal horizontal velocity of the aircraft, besides called the 1g-stall velocity. At this velocity the aircraft is winging with an angle of onslaught, which has the greatest lift coefficient ( CL-max ) . The second of import velocity is the maximal endurance velocity ( 2 ) . This is the velocity at which the aircraft has the lowest retarding force. The lowest retarding force consequences in the lowest fuel flow so that the aircraft can digest the longest clip with this velocity hence the maximal endurance velocity. Not merely is the maximal endurance velocity of import to cognize, save besides the maximal scope velocity of the aircraft ( 3 ) . At this velocity the relation between velocity and retarding force is at its lower limit, which makes the fuel flow per winging distance minimal. This consequences in the velocity at which the aircraft can wing the furthest. Finally the maximal horizontal velocity of the aircraft is besides show n on the diagram ( 4 ) . This is the velocity at which the upper limit available push is equal to the retarding force of the aircraft.Figure 3.X Performance diagram jet engine1 = 1g-stall velocity2 = soap. endurance velocity3 = soap. scope velocity4 = soap. horizontal velocityAll these different in operation(p) velocities vary due to certain conditions. The conditions that affect the public presentation of an aircraft with jet engines areThe heightThe ambient temperatureThe air velocityThe weight of the aircraftad 1 The heightAs we know, the ambient air force per unit area decreases as the height additions. With a diminishing air force per unit area the denseness besides decreases which consequences in less mint candy air flow into the engine and therefore less thrust. The retarding force of the aircraft is, and, self-sufficing of the height. With an increasing height, the retarding force remains the same while the true air velocity ( TAS ) increases because of a diminishing air denseness. This has every bit consequence that the stall velocity additions in TAS. The endurance of jet engines is changeless with the height and the maximal scope additions with an increasing height ( appendix 3.1 ) .ad 2 The ambient temperatureJet engines are limited by the RPM and the turbine gas temperature ( TGT ) of the engine. When the ambient temperature is high, the engine will make its maximal TGT Oklahoman than when the ambient temperature is lower. When the ambient temperature is comparatively low, the engine can run at higher Revolutions per minute before the TGT is reached, ensuing in more thrust. At high ambient temperatures the push of the engine varies with the temperature, but at comparatively low temperatures ( below ISA+15 ) the generated push is changeless with the RPM. At these temperatures the engine is called level rated.ad 3 The air velocityAs the airspeed additions, the produced push of the jet engine will cut shoot down due to an addition of the recess neural impulse retarding force. Air come ining the recess of the engine is slowed down and loses impulse due to compaction, before it is accelerated once more. This loss of impulse is called recess impulse retarding force and consequences in a decreasing push with an increasing air velocity. The addition of air velocity, nevertheless, besides consequences in more air mass per unit volume through the engine, which leads to an addition of push. These opponent effects consequence in an overall push, which varies depending on the engine & A acirc s design ( appendix 3.2 ) .ad 4 The weight of the aircraftThe weight of the aircraft besides has a important influence on the public presentation of an aircraft with jet engines. It does non impact the public presentation of the engine itself, but the whole aircraft. much weight of an aircraft consequences in more retarding force. To get the better of this retarding force and to maintain winging horizontal, the aircraft should increase its angle of onslaught or increase its air velocity. The public presentation diagram shows that an increasing weight of an aircraft has a negative consequence on the public presentation of the aircraft ( appendix 3.3 ) . The stall velocity additions with an increasing weight and the endurance and maximal scope will twain lessening with an increasing aircraft weight.3.1.3 Performance Turbo-prop EngineThe public presentation of a turbo-prop aircraft is about resembling to the jet aircraft. The turbo-prop engine is driven by a jet engine. In a turbo-jet engine the speed and force per unit area of the flummox gases create the push but in the turbo-prop engine merely a little sum of the push comes from the fumes gases. This is due to the fact that most of the energy has been absorbed by the turbine for driving the propellor. When ciphering turbo-prop public presentations the public presentation of a jet engine can be taken, merely affair where must be thought of is the propellor efficienc y.3.2 Most suited Piston aircraftFrom all the little Piston aircraft ( including turbo- and supercharged aircraft ) , there will be looked at the public presentation, fuel ingestion, scope, figure of riders, and the planetary follows to non sum the trump scorch engine and the beat out multi engine Piston aircraft. global cost are several variable costs such as fuel ingestion, set downing fees and an estimation of care. First a analyze will be made of single-engine Piston aircraft ( 3.2.1 ) and thenceforth a analyse of multi-engine Piston aircraft ( 3.2.2 ) . A concluding recommendation will demo the most suited aircraft of its type for the intents set in this chapter.3.2.1 Single engineIn this paragraph the most suited aircraft with a individual Piston engine is determent. A pre-selection is made with initial demands. Those demands are range, take-off distance, and monetary harbor. The following tabular start out ( put over & A acirc .aircraft comparing ) show which air craft meets the demands set earlier.& A Acirc station ( micromillimeter )Takeoff infinite ( foundation ) MTOWLanding keep ( sustainside ) MLWsoap sail face lift ( human foot )Cruising velocity ( karat )monetary prize ( dollar bill )Cessna P210N Turbo centurion II900600 euchre27.000193438.000Cessna Skyhawk SP6401.6301.33514.000124307.500Cessna Turno Skylane9711.3851.35020.000165398.100Cessna Turbo Stationair7031740139527.000164557.500Cessna Corvalis TTx1.2501.9002.64025.000235733.950Beechcraft Bonanza G369081.9131.45018.500176691.390Piper Matrix1.3431.0871.02825.000213757.000Piper Arrow8801.00062016.200137323.850Piper Archer LX5221.13592014.100128319.200cirrhus SR20785147885317.500155276.690 cirrus cloud SR221.1701594114117.500185380.000Cirrus SR22T9478221.14125.000214475.000Average9181357119820567174471515Table & A acirc .aircraft comparingWith the current demands the aircraft are able to acquire to their finishs and land safely within the budget. With the extra dema nds determent before in this chapter the most suited aircraft is explained.After those extra demands the Cessna P210N Turbo centurion II is left as the most suited aircraft. The Cessna P210N has a pressurized cabin, a maximal sail height of 27.000 foot, a conditions radio detection and ranging survival of the fittest and de-icing equipment. The Cessna is capable of easing siting for tail fin riders and has a high batch cruising velocity of 193 karats.In Annex & A acirc . ( Annual sum-up ) a comparing is made of the selected aircraft and the costs over 10 old ages. In this comparing the Cessna P210N is one of the more expansive aircraft but the lone aircraft that fits the demands needed for this type of concern trips. The initial costs of the Cessna P210N are approximative 343.600 euro and the variable costs with 300 flight hours yearly are 75.794 euro. Variable costs include fuel, airframe care, labour and parts, engine Restoration and sundry(a) costs. In ten old ages the sum costs will be about 1.101.607 euro.3.2.2 Multi engine Piston aircraftMulti engine Piston aircraft have better belongingss than individual engine Piston aircraft. There are many legislated multi engine Piston aircraft unremarkably used in the European general air power. However, some of these aircraft do non run into the managers demands stated in paragraph 3.2.1. The staying aircraft besides needed to hold a pressurisation system and de/anti ice equipment ( table 3.x )& A Acirc Range ( nanometer )Takeoff Distance ( foot ) MTOWLanding Distance ( foot ) MLWsoap sail elevation ( foot )Cruising velocity ( karat )monetary value ( dollar )Beechcraft 58P Baron13562200200020000200325.000Beechcraft G58 Baron12002500230020688192829.000Beechcraft 60 Duke10202200200030000214193.000Beechcraft B60 Duke11202200200030000214250.000Cessna 340A14052 cd220029800170299.000Cessna 41111302700250026000202135.000Cessna 414A132726002 cd30800183189.000Cessna 421A14882four hundred22002700019775.000Cessna 42 1C17122 cd220030200205249.000Piper PA31 Navajo11602200200029000165169.000Average12922380218027348194271.300Table 3.x Aircraft comparingThese aircraft are besides compared on estimated variable costs ( appendix .Multi engine Piston aircraft ) . The most pricey aircraft to buy, turns out to be the cheapest aircraft in a period of 10 old ages the Beechcraft G58 Baron. This aircraft will hold an estimated variable cost of 278 euro per flight hr. When runing 300 flight hours annually, the estimated sum costs of the Beechcraft G58 Baron are 1.479.660 euro in a period of 10 old ages.3.3 Jet aircraftThe most suited single- and multi-piston engine aircraft are found. The following aircraft type looked at is the jet engine. The jet engine has an recess, which sucks in the air the air is so quick compressed and fuelled to light. After ignition the air has a enormous change magnitude velocity, which propels the aircraft. There is a figure of jet aircraft presently used. Some of the aircraf t have merely one engine others could hold six. In the hunt of our aircraft we look at the individual engine jets and the jet aircraft, which have two engines. The jet aircraft with one jet is called a Single Jet engine aircraft ( 3.3.1 ) . The aircraft with two or more engines is called a multi-engine Jet aircraft ( 3.3.2 ) . For either type of aircraft the best aircraft is chosen in order to happen the best aircraft for our CEO.3.3.1 Single engineA individual engine jet aircraft is exceeding in its sort. The aircraft uses one jet engine, which propels the aircraft. This sort of aircraft is more luxury than their similar sized propellor aircraft. For illustration the aircraft has the option to hold a lavatory inside the aircraft. The downside of this sort of aircraft is that the initial cost of the aircraft is much higher than the propellor driven aircraft. The initial monetary value& A Acirc Range ( nanometer )Takeoff Distance ( foot ) MTOWLanding Distance ( foot ) MLWsoap sail e levation ( foot )Cruising velocity ( karat )monetary value ( dollar )Diamond D-Jet13502500190025.0002401.380.000Excel-Jet SportJet10001800180025.000& A Acirc 1.000.000Piper Jet Altaire13002.3002.00035.0003202.199.000Eclipse 40012502.0452.10041.000& A Acirc 1.350.000Cirrus peck SF5012001.6001.24528.0002101.000.000of these sorts of aircraft is about one jillion dollars and the monetary value per flight hr varies from 500 dollars to 700 dollars. Table 3.X shows the monetary set and specifications of five different individual jet aircraft.Three of the five aircraft are more dearly-won seen the initial monetary value and monetary value per hr. The monetary values of the Diamond D-Jet and the Piper Jet Altaire are significantly higher than the other three this will except both of them. The Excel-Jet Sportjet is pipe down a truly futuristic aircraft, the aircraft is meant to be a make it yourself aircraft so this will except the aircraft. The initial monetary value and monetary val ue per 3000 hours is comparable to the last two, but there is no know information about De-icing.Three of the five aircraft are now excluded from our picks, this will ensue in the determination between the Eclipse 400 and the Cirrus mountain SF50. two aircraft have alone expressions they both have a V-tail and one jet engine located between the V-tail. Both aircraft have luxury seats and the cockpit is futuristic for the pilot. The specifications are all tantrum for the attempt it has to follow with. The scopes of the aircraft are adequate to wing to every location and back without the demand of refuelling the aircraft. Both aircraft can wing the needed velocity to keep a maximal flight clip of two hours to any of the locations. also both aircraft have de-icing equipment the Cirrus plenty has metal boots and the Eclipse 400 has rubber boots.The difference between the two aircraft ballad in the initial cost and the cost per hr. The Eclipse 400 has an initial cost of 1.35 card inal dollars and the Cirrus Vision costs one million dollars. But the & A acirc ?per hr & A acirc A? monetary value of the Eclipse 400 is 80 dollars less than the Cirrus Vision. The first 3000 flight hours the Eclipse 400 is still more expensive. But the Eclipse is less expensive than the Cirrus Vision after 4375 flight hours. A decision can be made on these findings, the initial monetary value of the Eclipse 400 is 350.000 dollars more but the Eclipse will be less expensive after 4375 hours. If the CEO is winging the aircraft for a period of more than 5000 hours the difference in monetary value will be 50.000 dollars. The Numberss given are achieved doing engagement of simple math equations, which include initial monetary value electropositive cost per hr apparatus against the clip flown with the aircraft. All the monetary values for the cost including 3000 flight hours and the differences are given in dollars. In euros the entire monetary value for the Eclipse 400 will be 2 5.000 over two million and the entire monetary value for the Cirrus Vision will be 60.000 euros under two million. This is the initial cost of the aircraft plus the 3000 flight hours.However the initial specifications asked by the CEO are set on 3000 flight hours. After 3000 flight hours the Cirrus Vision is still less expensive than the Eclipse 400. So the Cirrus Vision is the chosen individual Jet aircraft.Table 3.X3.3.2 Multi engine jet aircraftMulti engine jet aircraft has plausible the best public presentation in airspeed and height compared with propjet and Piston engine aircraft. The advantage of runing a twin engine aircraft is the reliability to do a safe attack after an engine failure. The evil is that keeping two jet engines is more expensive alternatively of 1 jet engine. The purchase costs of an aircraft in the class & A acirc ?very visible radiation jet & A acirc A? starts from an approximate & A acirc 700.000. Tabel ten shows the most suited purchase options i n the class multi engine jet aircraft.& A Acirc Range ( nanometer )Takeoff Distance ( foot ) MTOWLanding Distance ( foot ) MLWsoap sail elevation ( foot )Cruising velocity ( karat )monetary value ( & A acirc )Maverick smartjet12501320144725.000277697.500Embrear bequest 50030004600210045.0006081.416.800Embrear bequest 45023004000200045.0005931.170.400Tabel tenIn add-on to the clients demand there is no suited aircraft in this class. The Maverick smart jet agrees the budget but is non equipped with a de-icing installing. Both Embrear Legacy aircraft agree the clients demands, and would run suddenly on the determined paths. The lone advantages are the cabin size which is intentional to transport up to eight people, and both aircraft require aviation of 2 pilots.3.4 Most suited turbo-propFrom all the little turbo-prop aircraft, there will be looked at the public presentation, fuel ingestion, scope, figure of riders, and the planetary costs to find the best scorch engine ( 3.4.1 ) and the best multi engine turbo-prop ( 3.4.2 ) aircraft. Global costs are several variable costs such as fuel ingestion, set downing fees and an estimation of care. Finding a suited aircraft that fulfils the in operation(p) demands within the budget is hard, because turbo-prop engines are expansive.3.4.1 Single engineIn this paragraph the most suited aircraft with a individual propjet engine is determent. Again a preselecting is made with the initial demands. The two functional aircraft are seen in tabular array .. ( Aircraft comparing ) .& A Acirc Range ( nanometer )Takeoff Distance ( foot ) MTOWLanding Distance ( foot ) MLWsoap sail elevation ( foot )Cruising velocity ( karat )MTOW ( confiscate )Pressurized cabinSeatingmonetary value ( dollar )Pilatus PC-68701.4441.03325.0001256.173& A Acirc No101.000.000Cessna move1.2951.16071525.0001868.000& A Acirc No111.600.000Table & A acirc .Aircraft comparingBoth aircraft are by all agencies able to transport adequate people. The Pilatus PC-6 does non suit the velocity bound and is hence non possible as concern aircraft for this operation. The Cessna Caravan does carry through the velocity bound but is a diminutive overpriced. The initial costs can be raised, if the aircraft turns out to be the best. The Cessna has de-icing equipment and conditions radio detection and ranging. The variable costs of the Cessna will be about 500 Euro per runing hr. Variable costs include fuel, airframe care, labor and parts, engine Restoration and assorted costs. The variable costs in ten old ages based on 300 flight hours a twelvemonth will be 1.500.000 euro. The operating costs of the Cessna Caravan in ten old ages will be about 2.753.721 Euro.The Cessna Caravan is the most suited individual engine propjet aircraft but does non suit the concern operation because there is no pressurized cabin available. Reasoning it can be said that in this monetary value class and the type of engine there is no suited aircraft for the corp oration & A acirc s demands.3.4.2 Most Suitable Multi-Engine Propjet AircraftFour different aircraft are found for the most suited Multi-Engine Propjet aircraft. The job is that the aircraft all inadequacy of the de-icing equipment needed for the most suited aircraft. There is an option on every aircraft to attach boots on the wings and the stabilizers. But the anti-ice equipment needed on the propellor blades is non included in any of the aircraft. In short the multi-engine propjet aircraft are excluded for the most suited aircraft, which would be recommended to the CEO. If we deny the fact that the de-icing equipment is non valuable plenty the aircraft are still excessively expensive to suit the budget. The budget is 1.5 million dollars and the cheapest multi propjet ( Hawker Beechcraft queer Air C90GTx ) aircraft costs 3.6 million dollars. excessively the monetary values per flight hr start from 500 dollars per hr boulder clay 690 dollars per hr. So the estimated monetary va lue for the undermentioned 3000 flight hours is non interesting for the CEO.A decision can be made harmonizing to the findings for the most suited multi-engine propjet aircraft. None of the found aircraft fit the parametric quantities, which are set up for the most suited aircraft.& A Acirc Range ( nanometer )Max sail elevation ( ft. )Max velocity ( karat )Cruising velocity ( karat )Cost pH( $ )Pressurized cabinPrice ( $ )Cost 3000FH( $ )De-IcingKing Air 250161035.000310& A Acirc 630Yes5.800.0007.690.000NoPiaggio P180 Avanti II147041.000402690Yes5.700.0007.770.000NoPiaggio P16691524.000220220540No5.000.0006.620.000NoKing Air C90GTx131130.000270208500Yes3.600.0005.100.000NoTable 3.X3.5 DecisionThere were six classs out of which the best aircraft is chosen. As there was no multi jet engine aircraft which fits in the managers demands, five aircraft where selected ( table 3.x ) .Range ( nanometer )Take Off Distance ( foot ) MTOWLanding Distance ( foot ) MLWMax Cruise Alt. ( foot )Crui se Speed ( karat )MTOW ( pound )SeatingsPrice ( euro )Costss per FH ( euro )Cessna P210 Turbo Centurion II90060050027.0001934.0005341.640251,16Beechcraft G58 Baron1.2002.5002.30020.6882025.5006646.620277,68Cirrus Vision SF501.2001.6001.24528.0002106.00071.528.000390Cessna Caravan1.2951.16071525.0001868.000111.248.000390Beechcraft King Air C90GTx1.3112.5522.36330.00020810.48582.808.000390Average1.1811.68214.2426.1382006.79771.314.452339,77Table 3.x Selected aircraftThe best three aircraft demand to be chosen out of these five aircraft. The Beechcraft King Air C90GTx is the first aircraft, which drops off because of the high purchase monetary value. The second aircraft, which drops off, is the Cessna Caravan the purchase monetary value does non suit in with the public presentations. This means that the top three aircraft are the Cessna P210 Turbo Centurion II, the Beechcraft G58 Baron and the Cirrus Vision SF50. The Cessna P210 Turbo Centurion II is the cheapest aircraft in a period of 10 old ages, it is nevertheless the smallest and the slowest aircraft. The Beechcraft G58 Baron is more expensive than the Cessna, it is nevertheless more curvaceous and has a higher sail velocity. The Cirrus Vision is the most expensive aircraft of the three. It provides nevertheless many services which can non be found at the other three aircraft. The seven seats arrangement can be easy adapted in a four seats agreement, which consequences in tonss of infinite and comfort. The cabin has an optional toilet and there is a planet phone connexion available. A worldwide conditions system is integrated in the Garmin GFC700 pilotage show. The Garmin GFC700 pilotage system besides supports RNAV, which is utile when voyaging with DME and NDB beacons is over. The Cirrus Vision fills the spread between high public presentation Pistons, traditional propjet twins and visible radiation concern jets.